Gas turbine engine airfoil with vane platform cooling passage
A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.
1. A stator vane for a gas turbine engine comprising:
an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface, a cooling passage arranged in the platform and including a circumferential passage fluidly connected to an inlet passage extending through an edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radically extending passage through the edge of the platform, and a void interconnected to at least one of the radially extending passage and the inlet passage.
2. The stator vane according to claim 1 , wherein the void includes multiple circumferentially spaced dead-ended radial passages separated circumferentially by ribs.
3. The stator vane according to claim 1 , wherein the platform includes a circumferential support to which the airfoil is mounted and an annular flange extends in the radial direction from the circumferential support, the cooling passage arranged within the annular flange.
4. The stator vane according to claim 3 , comprising inner and outer platforms radially spaced apart from one another and adjoined by the airfoil, the cooling passage provided in the outer platform.
5. The stator vane according to claim 4 , wherein multiple airfoils adjoin the inner and outer platforms.
6. The stator vane according to claim 2 , wherein multiple cooling passages extend to the edge provided by the annular flange, with at least one of the passages blocked by a plug weld to provide at least one of the dead-ended radial passages.
7. The stator vane according to claim 6 , wherein the cooling passage includes radial passages spaced from the edge and without a plug weld.
8. The stator vane according to claim 7 , wherein the cooling passage includes four dead-end radial passages.
9. The stator vane according to claim 1 , wherein the ribs are elongated in the radial direction.
10. The stator vane according to claim 9 , wherein a rib provides an L-shaped structure.
11. The stator vane according to claim 2 , comprising a core arranged within and providing the cooling passage, the core including multiple core portions extending beyond the edge of the platform.
12. The stator vane according to claim 11 , wherein a first connecting portion interconnects an inlet core portion providing the inlet passage and a first core portion, both inlet and first core portions extending beyond the edge.
13. The stator vane according to claim 12 , wherein a second connecting portion interconnects a third core portion extending beyond the edge to a circumferential core portion, which is also connected to the inlet and first core portions.
14. The stator vane according to claim 13 , wherein a third connecting portion interconnects radial core portions to one another, the radial core portions providing at least some of the dead-ended radial passages.